Slot Effect on Wing Aerodynamic Performance, ANSYS Fluent Simulation Training

$90.00 Student Discount

  • The problem numerically simulates airflow over an airfoil (NACA4421) with a slot on the leading edge using ANSYS Fluent software.
  • We design the 2-D model by the Design Modeler software.
  • We Mesh the model by ANSYS Meshing software, and the element number equals 260000.
  • We aim to study the aerodynamic performance of the wing (drag and lift).

Special Offers For Single Product

If you need the Geometry designing and Mesh generation training video for one product, you can choose this option.
If you need expert consultation through the training video, this option gives you 1-hour technical support.
The journal file in ANSYS Fluent is used to record and automate simulations for repeatability and batch processing.
editable geometry and mesh allows users to create and modify geometry and mesh to define the computational domain for simulations.
The case and data files in ANSYS Fluent store the simulation setup and results, respectively, for analysis and post-processing.
Geometry, Mesh, and CFD Simulation methodologygy explanation, result analysis and conclusion
The MR CFD certification can be a valuable addition to a student resume, and passing the interactive test can demonstrate a strong understanding of CFD simulation principles and techniques related to this product.



The present problem simulates the steady airflow over an airfoil (NACA4421) with a slot on the leading edge using ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

The present model is designed in two dimensions using Design Modeler software. The meshing of this present model has been generated by Ansys Meshing software. The total cell number is 260000.


In this project, steady airflow over an airfoil (NACA4421) is investigated By ANSYS Fluent software. Airfoil has a shape deformity (slot), which separates it into two different parts. A slot in the airfoil industry is used to optimize airfoil performance, including increased lift force.

The airfoil attack angle is equal to zero degrees. Air enters the domain with a velocity equal to 10 m/s. The drag and lift coefficients of this airfoil with zero attack angle are equal to 0.0755 and 0.3764, respectively.

Moreover, the standard k-epsilon model is enabled to solve the fluid equations.


At the end of the solution process, we obtain two-dimensional contours related to pressure, velocity, and eddy viscosity. For instance, the stagnation point in the pressure contour is evident where the pressure increases drastically at the airfoil’s leading edge.

Furthermore, by extracting detailed data using Fluent, Drag and lift coefficients of this airfoil are calculated to be equal to 0.0755 and 0.3764, respectively. Drag and lift coefficients for NACA4421 airfoil without slot with zero attack angles are reported to be equal to 0.06 and 0.1, respectively.

Both drag and lift coefficients are increased due to the presence of the slot.


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